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NACA-RM-L7C11
Aerodynamic characteristics of a 45 degrees swept-back wing with aspect ratio of 3.5 and NACA 2S-50(05)-50(05) airfoil sections
Year: 1947
Abstract: INTRODUCTION
The proposed use of swept and low-aspect-ratio wing plan forms and biconvex profiles to minimize compressibility effects at transonic and supersonic speeds has emphasized the need for data on the full scale aerodynamic characteristics of these wings at low mach numbers. A study is, therefore, being made in the Langley full-scale tunnel of the low-speed characteristics of wings having 10-percent-thick circular-are supersonic airfoils and various high-lift devices. As a part of this study an investigation has been made with a 45° swept-back wing of aspect ratio 3.5 and taper ratio 0.5.
The present paper presents the scale effect on the longitudinal aerodynamic characteristics, the aerodynamic characteristics in yaw, and the tuft studies for 0° and 3.7° yaw. The results of the effect of leading-edge and trailing-edge flaps on the aerodynamic characteristics of the wing will be presented in later reports.
The proposed use of swept and low-aspect-ratio wing plan forms and biconvex profiles to minimize compressibility effects at transonic and supersonic speeds has emphasized the need for data on the full scale aerodynamic characteristics of these wings at low mach numbers. A study is, therefore, being made in the Langley full-scale tunnel of the low-speed characteristics of wings having 10-percent-thick circular-are supersonic airfoils and various high-lift devices. As a part of this study an investigation has been made with a 45° swept-back wing of aspect ratio 3.5 and taper ratio 0.5.
The present paper presents the scale effect on the longitudinal aerodynamic characteristics, the aerodynamic characteristics in yaw, and the tuft studies for 0° and 3.7° yaw. The results of the effect of leading-edge and trailing-edge flaps on the aerodynamic characteristics of the wing will be presented in later reports.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:33:24Z | |
| date available | 2017-09-04T15:33:24Z | |
| date copyright | 01/01/1947 | |
| date issued | 1947 | |
| identifier other | OJMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/35025 | |
| description abstract | INTRODUCTION The proposed use of swept and low-aspect-ratio wing plan forms and biconvex profiles to minimize compressibility effects at transonic and supersonic speeds has emphasized the need for data on the full scale aerodynamic characteristics of these wings at low mach numbers. A study is, therefore, being made in the Langley full-scale tunnel of the low-speed characteristics of wings having 10-percent-thick circular-are supersonic airfoils and various high-lift devices. As a part of this study an investigation has been made with a 45° swept-back wing of aspect ratio 3.5 and taper ratio 0.5. The present paper presents the scale effect on the longitudinal aerodynamic characteristics, the aerodynamic characteristics in yaw, and the tuft studies for 0° and 3.7° yaw. The results of the effect of leading-edge and trailing-edge flaps on the aerodynamic characteristics of the wing will be presented in later reports. | |
| language | English | |
| title | NACA-RM-L7C11 | num |
| title | Aerodynamic characteristics of a 45 degrees swept-back wing with aspect ratio of 3.5 and NACA 2S-50(05)-50(05) airfoil sections | en |
| type | standard | |
| page | 25 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1947 | |
| contenttype | fulltext |